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MW Fly B22 AeroPower Quick Installation

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B22
AeroPower
QUICK INSTALLATION
Manual for B22
Revision 1.0 – 02/05/2013

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Summary of Contents for MW Fly B22 AeroPower

  • Page 1 AeroPower QUICK INSTALLATION Manual for B22 Revision 1.0 – 02/05/2013...
  • Page 2 Manual Q – Quick Installation MANUAL Q Before attempting any engine start carefully read Manual A containing important safety information. Not following safety procedures could cause severe injury or loss of life. Consult the aircraft instruction manual for more information on safety. Manual for B22 Revision 1.0 –...
  • Page 3 All information, illustrations, instructions and technical data contained in this manual has been upgraded before printing. MW Fly reserves the right to modify, correct or upgrade general data at any time without any obligation or prior consent from third parties. Publication of any part of this document without written consent of MW Fly is strictly prohibited.

  • Page 4: Table Of Contents

    Manual Q – Quick Installation Q.1. SUMMARY Q.2. INTRODUCTION Q.2.1. Statement Q.2.2. Consultation Notes Q.2.3. Identification Data A.2.4. MW Fly Authorized Service Centers Q.3. SAFETY Q.3.1. Statement Q.3.2. General rules Q.3.3. Modifications and accessory Q.3.4. Location and identification of components Q.4.
  • Page 5 Manual Q – Quick Installation Q.8.2. Operational limits and technical data Q.8.2.1 fluids capacity Q.8.3. Standard radiator and hoses Q.8.3.1. Installation Q.8.4. Recommended cooling fluid Q.8.5. Cooling system refilling Q.8.6. Fine setting Q.8.6.1. Cooling system air intake dimension Q.8.6.2. Measuring cooling fluid temperature Q.8.6.3.
  • Page 6 Manual Q – Quick Installation Q.11.2.1. Air filter Q.11.2.2. Air intake manifold Q.11.2.3. Throttle control cable Q.11.2.4. Components operative limits Q.11.3. General installation directive Q.11.3.1. Air intake manifold removal Q.11.3.2. Engine air intake Q.11.3.3.Cowling air intake Q.11.3.4.Throttle control system Q.11.4.Final setting Q.11.4.1.
  • Page 7 Manual Q – Quick Installation Q.14.2. Recommended lubricant Q.14.3. Refilling reduction box Q.14.4. Propeller Q.14.4.1. Polar moment of inertia Q.14.4.2.Propeller balance Q.14.5. Final setting Q.14.5.1. Gear oil temperature check Q.15. INSTRUMENTATION SENSOR Q.15.1. Flight instrumentation (HSA-M) Q.16. POST INSTALLATION CHECK AND FINAL TEST Q.16.1.

  • Page 8: Manual Q - Quick Installation

    Manual and the Additional Maintenance Manual. Manual and the Additional Maintenance Manual. B22 AeroPower engine has not received any certification for aeronautical use. B22 AeroPower engine has not received any certification for aeronautical use. B22 AeroPower engine has not received any certification for aeronautical use.

  • Page 9: Identification Data

    B.4.2.1.C. Q.2.3.1.P Deleting or modifying the serial number will revoke any warranty and obligation by MW Fly toward current owner. Provide the serial number on any request for an engine part or technical information. A.2.4. MW Fly Authorized Service Centers Contact the nearest service centre or web-site for any information regarding service, maintenance or spare parts.

  • Page 10: Safety

    Q.3. SAFETY Q.3.1. Statement The onus to install MW Fly B22 engine is at the sole discretion and responsibility of the Original Manufacturer, Home Builder or Aircraft Owner. MW Fly cannot assume responsibility for a successful installation in a specific airframe due to the variety of designs existing in the market.

  • Page 11: Technical And Operational Caracteristics

    Manual Q – Quick Installation Q.4. TECHNICAL AND OPERATIONAL CARACTERISTICS Q.4.1. Dimensions Dim ensional w it hout gear box Throttle control Ø1.2 bowden 3m length F L Y Upper position INTAKE EFFECT From radiator Center of Ø32 pipe mass Max heat transfer 36kW at take off To radiator Prop axis...
  • Page 12 Manual Q – Quick Installation Q.4.1.1.P Dim ensional w it h gear box Throttle control Ø1.2 bowden 3m length F L Y Upper position INTAKE EFFECT Prop axis Prop axis From radiator Center of Ø32 pipe mass Max heat transfer 34.5kW at take off To radiator Ø32 pipe...
  • Page 13 Manual Q – Quick Installation Ø116 Q.4.1.3.P Manual for B22 Revision 1.0 – 07/02/2013...

  • Page 14: Weights

    Manual Q – Quick Installation Version without gear box direction - direction + total Max dimension [mm] Max along X axis Max along Y axis Max along Z axis Q.4.1.1.C Version with gear box direction - direction + total Max dimension [mm] Max along X axis Max along Y axis Max along Z axis...

  • Page 15: Optional Accessory

    Manual Q – Quick Installation * data can be modified Q.4.2.1. Optional accessory Adapter for bed mount (4 pieces) 0.37 Kg Exhaust system ~ 5.1 Kg Coolant radiator kit ~ 1.7 Kg Auxiliar fuel pump 0.66 Kg Governor** Propeller with hub ** HSA-M (without wiring loom)** EH-M (Electric Hub Module) ~ 0.98 Kg...

  • Page 16: Permissible Load On Propeller Flange

    Manual Q – Quick Installation Ve r s i on w i t h g e a r b ox Q.4.4.1.P Version w it hout gear box Q.4.4.2.P Never manually rotate the propeller in the opposite direction. This operation can damage the automatic timing chain tensioners and also disengage the system on the engine starter.

  • Page 17: Operational Limits

    ECU temperature exceeds the value indicated in table Q.6.4.1.C, the ECU could be damaged and it is mandatory to send it to an MW Fly service center for control. The cooling system must be designed to guarantee that the engine will work at a temperature that is lower than the max temperature indicate in the table Q.6.4.1.C...

  • Page 18: Preparing For Installation

    Q.5.1. Engine handling Pay attention while moving the engine, use caution to prevent injuries and material damage. To lift the engine MW Fly has designed a special hook (code X285). The hook is wedged F L Y I NTAK E...

  • Page 19: Engine Position And Attachment

    Manual Q – Quick Installation Q.6. ENGINE POSITION AND ATTACHMENT Q.6.1. Assembly position The B22 engine must be fitted on the fuselage with the propeller axis horizontal or slightly inclined, only a small deviation is permitted. In all cases the engine sump must remain at the bottom.

  • Page 20: Description Of The Mounting Points

    Manual Q – Quick Installation Pusher application On ground In flight Rotation angle [deg] applied to: Pitch axis +3/-8 +10/-40 Bank angle +5/-5 +45/-45 Q.6.1.2.C Q.6.2. Description of the mounting points Built into the engine, there are nine mounting points. In a standard wall installation the mounting points are on the rear side labeled “R”.
  • Page 21 Manual Q – Quick Installation Version with gear box R1 Point R2 Point R3 Point R4 Point Axis on wall attachment point [mm] 137.5 -100 -137.5 -218.2 81.8 -218.2 81.8 Q.6.2.4.C Version with gear box L1 Point L2 Point L3 Point L4 Point Axis on bed attachment point [mm]...
  • Page 22 Manual Q – Quick Installation At t achment point s version w it hout gear box Point L4 Point L2 Thottle control - 180° tilting cable R points level R points level 463.4 463.4 Point L4 Point L2 Center of mass Point L3 Point L1...
  • Page 23 Manual Q – Quick Installation At t achm ent point s version w it h gearbox Point L4 Point L2 Throttle control - 180° tilting cable R points level R points level 539.4 539.4 Point L4 Point L2 Center of mass Point L3 Point L1...

  • Page 24: Maximum Load Permitted On The Attachment Point

    Manual Q – Quick Installation Q.6.3. Maximum load permitted on the attachment point The engine mount should be designed to not exceed the max allowable load on the attaching point. Q.6.3.1. “R” attachment point To attach the engine use only M10x1.5 class 8.8 bolts, partial threaded (shank) minimum length 70 mm plus the length of mounting point on the engine frame.

  • Page 25: Attachment On Engine Cradle

    Manual Q – Quick Installation Using the “F” attachment point it is mandatory to use a damping element between the engine and the engine frame to prevent stressing the aircraft frame with excessive vibration. Q.6.4. Attachment on engine cradle The installation of the engine must be done as described below: Necessary tools and material: 1.
  • Page 26 Manual Q – Quick Installation  Insert the four bolts through the attachment points on the engine frame and then in the attachment points on the engine.  Using tool [3] screw the four bolts to align and pull the engine closer to the engine frame. While turning ensure that the dampers stays inside their housings in the attachment points.

  • Page 27: Exhaust System

    Manual Q – Quick Installation Q.7. EXHAUST SYSTEM Exhaust system installation: make sure that exhaust manifold and muffler do not rub on airframe, cowling or engine. Q.7.1. Standard exhaust system Q.7.1.1. Description AeroPower standard exhaust system (code C075) can be used in both pulling (Q.7.1.1.P) and pushing (Q.7.1.2.P) application.
  • Page 28 Manual Q – Quick Installation Cyl #4 Cyl #2 Cyl #3 Cyl #1 Q.7.1.3.P  Insert the four exhaust manifolds into the muffler as shown in picture Q.7.1.4.P until the pipe reaches the stop inside of the housing. Cyl #4 Cyl #2 Cyl #3 Cyl #1...

  • Page 29: Operational Limits

    Manual Q – Quick Installation Manual Q – Quick Installation Manual Q – Quick Installation  Using pliers [2] rotate the far end of the springs 90°.  Using pliers [2] rotate the far end of the springs 90°.  Using pliers [2] rotate the far end of the springs 90°. ...

  • Page 30: Original Accessories

    Manual Q – Quick Installation Manual Q – Quick Installation Manual Q – Quick Installation generated by propeller and aircraft forward speed on the exhaust system is enough to keep the generated by propeller and aircraft forward speed on the exhaust system is enough to keep the generated by propeller and aircraft forward speed on the exhaust system is enough to keep the temperature under the operating limits, if that is not enough, consider an additional air intake on temperature under the operating limits, if that is not enough, consider an additional air intake on...

  • Page 31: Cooling System

    Manual Q – Quick Installation Q.8. COOLING SYSTEM Q.8.1. Description Cylinder Cylinder Tem perat ure Tem perat ure Head Head sensor sensor Double effect valve Radiat or Vaso espansione Wat er t ank Over full T< 75°C T> 75°C Therm ost at e Supplied (st andard equipment ) Cold circuit Opt ional...

  • Page 32: Q.8.2. Operational Limits And Technical Data

    Manual Q – Quick Installation Q.8.1.1.P Q.8.2. Operational limits and technical data Maximum coolant temperature in flight 102 °C  Minimum coolant temperature in flight 72 °C  Typical coolant temperature in flight 87 °C  Minimum coolant temperature in storage -18 °C (standard factory mix) ...

  • Page 33: Q.8.3. Standard Radiator And Hoses

    Manual Q – Quick Installation Manual Q – Quick Installation Manual Q – Quick Installation Standard radiator Standard radiator Standard radiator 0.55 L 0.55 L 0.55 L    Standard silicon manifold for radiator Standard silicon manifold for radiator Standard silicon manifold for radiator 0.4 L 0.4 L...

  • Page 34: Q.8.4. Recommended Cooling Fluid

    Manual Q – Quick Installation  Fasten the silicon manifold to the power manifold using [1] and the collar clamps supplied with the radiator kit. Tighten the collar clamps on the manifold with a maximum tightening torque of 5Nm; a higher value of tightening torque could damage the manifold. ...

  • Page 35: Q.8.5. Cooling System Refilling

    Manual Q – Quick Installation The engine with the radiator installed and the cooling system filled using a mixture of 33% of antifreeze will guarantee an antifreeze protection up to -18°C. Using the engine in colder weather necessitates a change to the coolant mixture. Avoid using the engine at temperature higher than the maximum allowed: this can damage the head gasket and can cause excessive piston wear.
  • Page 36 Manual Q – Quick Installation Expansion tank Filling manifold F L Y INTAKE EFFECT Q.8.5.3.P  Unscrew the pump bleeding plug located on the left side of the rear cover (the filling manifold partially hides the screw). Add the coolant until the coolant runs out from the pump bleeder hole.
  • Page 37 Manual Q – Quick Installation After the first engine startup it is necessary to purge the cooling circuit again as initially done in (Q.16.2.). To remove any remaining air from the circuit, follow the procedure indicated. Pay close attention when warming up the engine as air remaining in the cooling system can cause an inaccurate coolant temperature reading from the sensor on the cylinder head.

  • Page 38: Q.8.6. Fine Setting

    Manual Q – Quick Installation Q.8.6. Fine setting Q.8.6.1. Cooling system air intake dimension We do not have a standard size for the cooling system air intake because radiator air flow depends a lot with the position of the air intake on the cowling and with aircraft cruise speed. In any case, the same criteria for dimensions are still valid for most of the applications, and those are as follows: Place the air intake close to the propeller plane.
  • Page 39 Manual Q – Quick Installation  Repeat all the above instructions until no anomalies occur.  Do a flight test and check the coolant temperature during flight and especially during take- off. During the flight test, keep in close proximity to the airfield in case you need to do a precautionary or emergency landing.

  • Page 40: Q.9. Lubrication System

    Manual Q – Quick Installation Q.9. LUBRICATION SYSTEM Unless specifically requested, the engine is normally supplied without engine oil and gear box oil. Before starting the engine for the first time it is mandatory to fill the engine and gear box with the correct engine oil grade as illustrated in paragraph Q.9.4.

  • Page 41: Q.9.2. Operating Limits And Technical Data

    The prescribed lubricant is SYNAVIO ME 40 Engine Lubricant. This oil has been specifically formulated for the MW Fly AeroPower engine. Avoid the use of different oil from SYNAVIO ME 40, even with same specifications and same thermal viscosity as no other oils have been sufficiently tested.

  • Page 42: Q.9.4. Refilling Method

    Manual Q – Quick Installation °C Unigrade Mult igrade Q.9.3.1.C The decision to use oil with a thermal degree different from the one recommended is based on the oil temperature in flight conditions: in case the oil temperature (in working condition) climbs too high it is necessary to use oil with a higher thermal specification.
  • Page 43 Manual Q – Quick Installation Q.9.4.1.P Check the oil quantity using the dipstick integrated in the oil filler cap. On the dipstick two marks indicate the minimum and maximum oil levels as show in picture Q.9.4.2.P. Q.9.4.2.P The oil level should be checked when the engine is cold and after waiting at least 5 minutes after each top-up to allow oil to settle in the oil sump.

  • Page 44: Q.9.5. Final Setting

    To verify a correct installation keep checking the oil pressure during steep banking and steep climbing on the first flight test. Lubrication system on B22 AeroPower is not certified for aerobatic flying. Q.9.5.1. Engine oil pressure sensor check The engine oil pressure sensor is located on the top left side of the crankcase, plug size M10x1.

  • Page 45: Q.10. Fuel System

    Manual Q – Quick Installation Q.10. FUEL SYSTEM Fuel and fuel vapor are highly flammable and harmful if inhaled. All operations and intervention in the presence of fuel must be done in an open area with good ventilation and far away for any open flame or heat sources. Q.10.1.

  • Page 46: Q.10.2. Operational Limit And Technical Data

    Manual Q – Quick Installation Q.10.2. Operational limit and technical data The firewall and fuselage fuel system must be made using high quality components and following the instructions given in this manual. It must guarantee good engine performances under any operating conditions and limits.

  • Page 47: Q.10.2.3. Fuel Selector Valve

    To simplify the construction of the fuel To simplify the construction of the fuel To simplify the construction of the fuel line, MW Fly has designed the FD-M line, MW Fly has designed the FD-M line, MW Fly has designed the FD-M (Fuel Delivery Module).

  • Page 48: Q.10.3.2. Installation

    Manual Q – Quick Installation The position of the fuel inlet and outlet can be rotate 180 degrees (see picture Q.10.3.1.P). Both the fuel inlet and outlet use M12x1.5 fittings. Q.10.3.2. Installation Necessary material and tools 1. Torque wrench 2. Allen key 6 mm 3.
  • Page 49 Manual Q – Quick Installation Q.10.3.2.P The hole size on bolts to be used is left to the discretion of the Aircraft-Builder. The standard hole size for the FD-M back plate is 6.5 m/m. No rubber mounting is required.  Fix the FD-M case to the firewall and tighten the screws at the correct tightening torque. If necessary use thread-locker.

  • Page 50: Q.10.4. Installation And Dimensions

    Manual Q – Quick Installation Before starting the engine verify under pressure that no trace of leakage is found in the entire fuel system: remove the FD-M cover and verify of no leakage inside the FD-M module. Q.10.4. Installation and dimensions The fuel system must be in compliance with local Aviation Legislation in the Country where the engine will be used.
  • Page 51 Manual Q – Quick Installation  Remove the intake manifold from the engine following the instructions in paragraph Q11.3.1. For the fuel delivery lines, connect a prescribed hose or tube from the FD-M module to fuel distributor/regulator unit mounted on the top of the engine. Use a prescribed hose on the distributor/regulator valve return line.

  • Page 52: Q.10.5. Recommended Fuel

    Using fuel with lower octane rating than one prescribed can cause damage to the mechanical engine components. In case of accidental use of this type of fuel, it is mandatory to send the engine to an MW Fly authorized maintenance center. Q.10.6. Fuel circuit purge An air purge must be done every time work has been carried out on fuel system.

  • Page 53: Q.10.7. Final Setting

    3.5 bar. If the fuel pressure value is not correct and verified, do not fly and contact an authorized MW Fly service center.  With the engine running, switch on the auxiliary fuel pump. The fuel pressure should increase by no more than 0.1 bar, both with the engine in idle condition and at full throttle.
  • Page 54 Manual Q – Quick Installation never exceed 48°C during flight and shouldn’t climb over 65°C when the engine stops. To install a fuel temperature sensor follow the instructions indicated in the paragraph A.16.6 in the installation manual. To verify the fuel temperature, use the following procedure: ...

  • Page 55: Q.11. Air Intake System And Engine Ventilation

    Any modification of the Ram Intake Tube System is STRICTLEY PROHIBITED. Any modification must be approved by MW Fly in writing. It is important to avoid any water depositing in the intake manifold filters, both during the flight and on the ground.

  • Page 56: Q.11.2.3. Throttle Control Cable

    Manual Q – Quick Installation Q.11.2.3. Throttle control cable Throttle cable description and size. Inner wire material stainless steel 49 strands  Inner wire dimension D1.2 mm  Inner wire strength 800 N  Protective coating polyethylene  Minimum curve radius 150 mm ...
  • Page 57 Manual Q – Quick Installation Manual Q – Quick Installation Manual Q – Quick Installation Removal procedure Removal procedure Removal procedure  Some engines are fitted with air temperature sensors already mounted on the #1 bank ram  Some engines are fitted with air temperature sensors already mounted on the #1 bank ram ...

  • Page 58: Q.11.3.2. Engine Air Intake

    Manual Q – Quick Installation Installing air intake manifold  Recognize right intake manifold from left side; the MW Fly label is riveted on the right side cylinder head intake manifold and should be readable when viewed from propeller side.

  • Page 59: Q.11.3.4.Throttle Control System

    Manual Q – Quick Installation Q.11.3.4.Throttle control system On each throttle, two springs keep the butterfly in a fully open position. Pay attention during installation and the final setting on the throttle control system. There are two possible positions to fix the throttle Bowden cable splitter. Install it with the control cable facing down or up.

  • Page 60: Q.11.4.Final Setting

    Manual Q – Quick Installation  Use nylon cable-ties [3] to fix the throttle Bowden cable to the engine mount or to the air frame without compressing the cable.  Check that the cable does not touch any hot part of the engine or any sharp edges and does not rub on any abrasive part of the aircraft.

  • Page 61: Q.11.4.2. Manifold Pressure Check (Map)

    Manual Q – Quick Installation Q.11.4.2. Manifold pressure check (MAP) The two cylinder heads have the throttle body connected by a compensation tube. On the tube two pipes bring air pressure data to the ECU and fuel pressure regulator. Instructions on how to connect MAP sensor are found in section A.16.
  • Page 62 Manual Q – Quick Installation Q.11.4.2.P ECU temperature limits are illustrated in section Q.12.3.1. When the maximum ECU temperature value is exceeded a way must be found to remove the hot air from engine cowling compartment by either inducing more cold air in or discharging the hot air.

  • Page 63: Q.12. Injection And Ignition System

    Manual Q – Quick Installation Q.12. INJECTION AND IGNITION SYSTEM Q.12.1. Description If during flight the ECU warning light switches on it is mandatory to land as soon as possible, even if the engine is running without any obvious problem. Q.12.1.1.

  • Page 64: Q.12.2. General Characteristics

    Manual Q – Quick Installation Manual Q – Quick Installation Manual Q – Quick Installation Q.12.1.2.C Q.12.1.2.C Q.12.1.2.C Q.12.2. General characteristics Q.12.2. General characteristics Q.12.2. General characteristics ECU Dimensions ECU Dimensions ECU Dimensions 101x83x29 mm 101x83x29 mm 101x83x29 mm  ...
  • Page 65 Manual Q – Quick Installation Exceeding the ECU maximum operating temperature, when the engine is running, can cause a sudden stoppage of the engine, and damage to the ECUs. To measure the ECU temperature, proceed as follows:  Do the testing with air temperature not over 25 °C. ...

  • Page 66: Q.13.Electrical Loom

    Manual Q – Quick Installation Q.13.ELECTRICAL LOOM All engines are supplied with the engine wiring loom installed on the engine. The section of the wiring loom from the cockpit to the engine plug must be prepared by the builder of the aircraft respecting the following instructions: Q.13.1.

  • Page 67: Q.13.1.5. Cockpit Fuses

    Manual Q – Quick Installation Manual Q – Quick Installation Manual Q – Quick Installation Switch operation Switch operation Switch operation NO <NC> NO <NC> NO <NC>    Panel hole dimension Panel hole dimension Panel hole dimension D16 mm D16 mm D16 mm ...

  • Page 68: Q.13.2.2. Installation

    Manual Q – Quick Installation Q.13.2.2. Installation The EH-M is supplied with all components required for installation. Materials and tools required 1. Electric Drill with drill bit 5.5 mm 2. Hex key 8 mm 3. Hex key 10 mm 4. Open end wrench 10 mm 5.

  • Page 69: Q.13.3. Electric Diagram

    This harness must be made according to the drawing in section Q.13.3. Q.13.3. Electric diagram When the B22 AeroPower is installed together with the Electrical Hub Module (EH-M) and the Fuel Delivery Module (FD-M) the following connections have to be made by an experienced aircraft builder: ...
  • Page 70 Manual Q – Quick Installation ENGI NE PIN-OUT COCKPIT PIN-OUT POWER DESCRIPTION DESCRIPTION ECU1 SWITCH Vbatt+ GEN COCKPIT POWER VBatt+ ECU 1 Start Vbatt+ INJ 1/2 ECU1 CAN L relay N.C. FUEL PUMP RELAY VBatt COIL 1/1 START SWITCH Vbatt+ ECU 2 ECU2 CAN H N.C.

  • Page 71: Q.13.4. Implementation

    Manual Q – Quick Installation Q.13.4. Implementation The construction of the wiring harness must be carried out by an approved technician using the appropriate tools and aviation standards. The cable loom must be secured safely in order to avoid damage caused by: mechanical stress, excessive vibration, chafing, staying clear of exhaust system hot spots and causing no obstruction to the controls.
  • Page 72 Manual Q – Quick Installation # pin Description Cable Size [mm Connect to 1-14 Generator charge Fuse 30A (1) Vbatt+ ECU 1 0.75 Fuse 5A ECU 1 (1) Vbatt+ injector #1 ECU2 Fuse 10A injector 1/2 (1) Main pump signal 0.75 Main pump relay (2) Vbatt+ coil #1 ECU1...
  • Page 73 Manual Q – Quick Installation Command OFF main master relay 0.75 HSA-M (Mas 2) Command ON aux. master relay 0.75 HSA-M (Mas 3) Command OFF aux. master relay 0.75 HSA-M (Mas 4) Vbatt+ HSA-M 0.75 Breaker 1A HSA-M (Main 1) Vbatt+ main fuel pump Breaker 10A main pump (1) Vbatt+ aux fuel pump...
  • Page 74 Manual Q – Quick Installation ECU 2 switch (2b) Vbatt+ aux pump Breaker 10A aux pump (1) Aux pump switch (1) Vbatt+ aux pump Breaker 10A aux pump (2) ECU 1 switch (2b) Vbatt+ aux pump ECU 2 switch (1b) Breaker aux pump (2) Vbatt+ aux pump FD-M (4)

  • Page 75: Q.13.5. Connection Of The Electrical Components

    Manual Q – Quick Installation GND aux pump FD-M (3) GND start relay Start switch GND master switch Master switch (GND) GND ECU 1 0.75 ECU 1 switch (2a) GND ECU 2 0.75 ECU 2 switch (2a) Battery (+) Vbatt+ main master relay Main Master relay Battery (-) POWER GND(aircraft frame)

  • Page 76: Q.13.5.2. Generator And Voltage Regulator

    If, even in this condition, the operating temperature of the voltage regulator is over the limit it will be necessary to remove it from the engine. In this case contact an MW Fly service center.

  • Page 77: Q.14. Reduction Gear Box

    Manual Q – Quick Installation If the starter is used for a long period, it will overheat. Do not use the starter for periods longer than 10 sec and wait at least 30seconds between consecutive tries to start the engine. If the engine doesn’t start in few tries do not persist. Q.14.

  • Page 78: Q.14.1.2. Governor

    Manual Q – Quick Installation Ø125 Q.14.1.1.P Propeller flanges with different attachment holes as well as a propeller shaft probe are available on request. It is possible to use a 150 mm maximum extension on the propeller shaft. The extension should be perfectly coaxial and concentric with the propeller shaft to avoid any imbalance load on the propeller shaft.

  • Page 79: Q.14.1.3. Oil Capacity

    Manual Q – Quick Installation ** data not available Q.14.1.3. Oil capacity Quantity of gear box without governor 300 cm³  Quantity of gear box oil with governor ** --- cm³  Tolerance on oil level ±50 cm³  ** data not available Q.14.2.

  • Page 80: Q.14.4.2.Propeller Balance

    3 gram for static and not over 0.5 gram/meter dynamically. MW Fly decline any responsibility for damage or body injuries done by the use improper propeller, or propeller not correctly installed or out of balance.

  • Page 81: Q.14.5.1. Gear Oil Temperature Check

    If the overheating of the gear box oil is in combination with an unusual noise in the gear, it is mandatory to contact an MW fly service center to check the gear box. Q.15. INSTRUMENTATION SENSOR...

  • Page 82: Q.15.1. Flight Instrumentation (Hsa-M)

    Manual Q – Quick Installation In no cases should the installation of the sensors compromise the engine harness: it is forbidden to make any connections or derivation from the engine harness. Do not modify the original engine harness as it could compromise the safety of your installation.

  • Page 83: Q.16.2. First Start-Up

    Manual Q – Quick Installation Q.16.2. First start-up Only for the first start up of the engine it is necessary to follow all the below instructions:  Switch on the master relay to power on the electrical system.  Switch on the instrumentation. ...

  • Page 84: Q.16.3. Installation Final Test

     When the engine is turned off, check that there is no leakage of coolant or oil. In case there is a leakage of coolant or oil find the origin and contact an MW Fly authorized service center. Q.16.3. Installation final test The installation tests have two different goals.

  • Page 85: Q.16.3.3. In Flight Test

    Manual Q – Quick Installation Q.16.3.3. In flight test In the below table there are indicated the main cautions to follow in the first 15 hours of flight. Main caution for the first 15 hours of flight Keep the engine at maximum RPM within 60 seconds, and only in take off condition In flight condition keep the engine at least 300 RPM under the max continuous power with MAP lower than 26 inHg...

  • Page 86: Q.17. Manual Update List

    Manual Q – Quick Installation Q.17. MANUAL UPDATE LIST Version Pertinence Paragraph Page Data of change From #001911 Q.1. Sommay 02/05/2013 From #001911 Q.2. Introduction 02/05/2013 From #001911 Q.3. Safety 02/05/2013 From #001911 Q.4. Technical and operational 02/05/2013 characteristics From #001911 Q.5.

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